Adjustable cowling closure



Nov. 18, 1941.

ADJUSTABLE COWLING' CLOSURE Filed Aug. 25, 1958 s Sheets-Shget 1 INVENTOR5 ALFRED E LEVENDOS CHAQL F.Zl

YMO

ES MMERMAN ND P. HOLL DJr.

A. E. LEVENDOSKI ETAL 2,253,465 I Nov. 18, 1941.

ADJUSTABLE COWLING CLOSURE Filed Aug. 25, 1938 3 Sheets-Sheet 2 6h FIG. 5.

' INV/ENTORS ALFRED ausveuoosm cHAnLs F. ZIMMEQNAN 5/ A. E. LEVENDOSKI HAL 3 3 Nov. 18, 1941. A. E. LEVENDOSKI EIAL ADJUSTABLE COWLING CLOSURE 3 Sheeis-Sheet 5 Filed Aug. 25, 1938 FIG-.8.

INVENTORS ALFRED E. L CHADLES nA ON DOS-KI MMEQMAN a n HOL EVEN F. Zl

LA DJn famed Nov. 18, 1941 UNITED STATES PATENT OFFICE amass amus'raam comma cmsuar.

AIME.

Buffalo, and Charles F.

Mendel",

and Bana H m 1 K more, N. Y,

Curtias-Wright Corro- This invention relates'to adjustable closures. id is particularly concerned with an adjustable osure adapted for use with aircraft.

An object of the invention is to provide a reamlined adjustable fairing for use with a all! used with radial aircraft engines, but for achine gun or blast tube thereof which prothepurpose of this invention, the cowling It may udes, from a forward part of the aircraft. In likewise be considered as representing-a forward-- ilitary aircraft, fixed machine guns are mount- 1y disposed external aircraft surface. such as a l for forward firing and are located in one wing, fuselage, or landing gear fairing. A blast, several positions such as, in the wing leading tube ll forming a forward prolongation of a gun lge, in landing gear fairings, or in the cowling barrel l2 projects through the surface of the bich embraces an aircraft power plant. The cowling it to a point forward thereof, and to pro-, :ening in the aircraft surface through which the vide for lateral and vertical adjustment of the m or blast tube projects must be of somewhat blast tube II, th e wlln 1 Df vid with e rger diameter than the gun or tube to allow for 1 streamlined fairing l3 deflning at its forward ranges in the aiming position of the gun. For end a substantially circular aperture, the edges stance, the guns are o nted in cradle hi h of which have clearance with respect to the re adjustable with respect to the aircraft wing tube II. To the forward edge of the-fairin J i order to bring the line of tire of the gun into is rotatably attached a hemispherical element It certain relationship with the axis of symmetry n n n ric op ning ii. to the edges of E the airplane, and accordingly, the extending which in turn, a concentric spherically segmenld .of a gun barrel may move an appreciable tel element It is rotatably attached. The seg-. istance with respect to the surface of the air-, e has 811 pen I? h vln 'li l or n raft, the aircraft havingan' opening approclearance with respect to the blast tube ii. The riate to the chang in position of th gun relements it and it together provide a substanel. In modern high speed aircraft, such forward penings are undesirable, as they would induce nnecessary drag and a considerable blast of air "ithin the aircraft structure, and a closure for ac space between the barrel or tube and the dges of the aircraft opening is desirable. The arm of this closure should lend itself to proper treamlining and accordingly, a further obiect f the invention is to provide an adjustable be point where they project from the surface f an aircraft.

Further objects and advantages will be an ent from a reading of the annexed specification nd claims, together with an examination of the .ccompanying drawings, in which:

Fig. 1 is a side elevation of a portion of an airraft power plant cowling indicating a gun blast ube and a forward fairing and closure therefor;

Figs. 2, 3 and 4 are front elevations of cowling egments showingthe blast tubes in diiferent poitions of adjustment with respect to the cowling ind showing the adjustable closure in approrriate positions;

Fig. 5 is an enlarge'i fragmentary section of one unbodiment of adjustable streamlined closure; Fig.6isasectionomthe lineHofFig.5,' ind and 8 areenlarged fragmentary sec- 5.5

tions showing alternative arrangements of an adjustable closure.

In the figures, ll represents anaircraft power plant cowling of annular form as is conventiontially streamlined nose for the fairing I! regardless of the relative rotational adjustment there: of. By the eccentric openings respectively formed in the elements It and it. the tube ll may be 10- cated in sundry positions, as shown in Figs. 2, 3 and 4. The elements I4 and it are rotated with respect to each other and with respect to the fairing [3 so that the blast tubeopening I! may lie either concentric with the fairing It or eccentreamlined closure for guns or blast tubes at fihel'ewmmws Figs. 5, 6, 'l-and 8 show various embodiments of detailed devices, Fig. 5 including the element ll screwed to a collar 2|! fixed to the fairing IS. The eccentric opening it thereinds formed with screw threads to receive complementary screw threads on the segmental element It. The element it may be rotated upon the screw threads with respect to the element It, and likewise, the

element It may be'rotated on its screw threads with respect to the collar 20. To' prevent inadvertent rotation of the several parts, a spring drag 2| bears upon the element II and is screwed to the collar 20, as at 2'2, and likewise, a spring drag 23, attached to the element ll by a screw -24, bears upon the inside of the element It.

In Flg 'l the fairing I3 is provided with a spherically segmental forward end 26 within which a spherical segment 21 ishested and within the latter, in turn, smaller spherical segment 20 is disposed. These several segments, as, 212

'- segments."

2 I 2,asa,4es V and 28 are concentric-and are slidable upon one is passed for lateral and vertical adjustment rel; A another so that the blast tube opening il' in the ative to the aircraft.

smaller segment 28 may be moved to any appropriate position within the limits defined by the diameter of the forward opening in the segment 21. To hold theseveral segments in proper position, the blast tube is provided with an abutment II, and the smaller segment 28 is provided with an abutment II, a compression spring 82 extending between the abutments and tending to urge the small segment 28 forwardly, vthus holding the several segments in their proper dispositiom When adjustment of the blast tube ii is eifected, the several segments simply slide upon one another and it is unnry to rotate them with 'respectto'eachother,

In Fig. 8, the fairing it is provided with annular spherically segmental elements ll and II defining between the nested elements a spherical gap, the segments supportinganother spherical segment 36. The segment it is slidable and rotatable with respect to the segments -34 and II, the openings in the several segments being ap- Probriate to the size of the blast tube ii and .to the range of movement which is its proper adjustment.- in this last no spring is necessary since thesegment l6 rearward, displacement by the concentric segment II, The segment assembly comprising the units 14, II and It, may be unitary, and-may be embodiment,

for

asinthesho i tofrigr'l," is held from inadvertent 4. In an aircraft cowling having a slantez forward portion, a fore-and-aft open-ended tub faired thereto, a slender cylindrical element pro Jecting through said tube forward of its oper end, the element being adjustable laterally ans vdrtically within said tube; and a closure 10] the forward end of said tube comprising concentric spherical segments one attached to the edge:

- of the tube and rotatable erelative thereto and having an eccentric opening, and another. closely embracing the cylindrical element and movable over a surface of the first segment.

5. In an aircraft cowling having a slanted forward portion, a fore-and-aft open-ended tube faired thereto, a slender cy element projecting through said tube forwardof its open end, the element being adjustable laterally and vertically within said tube; and a closure for the forward end of said tube comprising concentric spherical segments one attached to the attached as a unit to the forward end of the fairing II by suitable screws 31 ,or' other appro- Driate devices. v 2

While we. have described our invention in detail in its present preferred embodiment, it will be obvious to those skilled 'in the art, after understanding our invention, that various changes and modifications may be made therein without departing from the spirit or scope thereof, We

modiiicationsand changes. v

We claim as our invention",

1. In aircraft having-fa substantially opening, a spherical segment-rotatably disposed adjacent the edge of the o and having an eccentric circular opening; and a second spheri segment spherically concentric with the first, r'otatably disposed in the opening of the ilrst'segment and having an opningbccentric to its segment circumference, where the center of aim in theramded claims to cover all gsuch .m t penmgn adjustable-radially and ansuiarly relative the center of the aircraft .opening by rota one or more of 2.--In a closure for an openingin a forwardlyfacing part of an aircraft; a plurality of relativelymovable'concentric spherical segmentsof graduated base diameter nested androtatable relative to one another, successive segments having eccentric openings of,graduated circular edges of the tube and rotatable relative thereto and having an eccentric opening, another closely embracing the cylindrical element and movabg overasurfaceofthe'firstsegmenhandmeand to'hold the segments in concentric relation.

I 8. Inanaircraft cowlinghavingaslantedfdraf ward portion,a fore-and-aftopen-ended tuba faired thereto, a slender cylindrical element pro lecting through said tube forward of its own end, the element being adjustable laterally and vertically within said tubepand a closure for the forward end of said tube comprising a first spherical segment rotatably carried by the tube at its open end. said segment having an eccentric opening, and a second spherical segment rotatflttedtosaid'element.

wardbortion, a fore-anddiameter fitted to -the bases of the next smaller ts, the smaliest-openingof the. smallest se ment being adapted. to embracea cylindrical element projecting said i opening being asto position through relative motion of "segments relative, to one s. In -mm was enlarged in a forwardly facing part of an aircraft, a Dlurali of consults-1c spherically formed segments, each larger segment having an eccentric opening to the edges of which smaller segment is 'rotatablysecured, the smallest segment having an which a cylindrical element fairedthereto,aslender ably carried by the first at the edge ofits opening,;said second segment having an eccentric opening through which saidcylindrical element sm s r passes. g r

'L In an aircraftcowling having a slanted forward portion. a fore-and-aft open-ended tube cylindrical elementproiecting through said tubeforward of its open end, the element being adiusthble laterally and 'verticallywithinsaid'tube: aclosure forthe forward end of said tube eomprising eontentric spherical segments the flrstsecured at-its outer edgetothe'tubeandhavinganeniargedopen- 'an'da second segment overlapping and movable oyer the oneand'having an opening closely vinga slanted foropen-ended tube faired thereto, a slender cylindricalelement projectingthmughsafiftubeforward ofits openend;

'adjusiable'laterally and vertube a closm'e for the forcowling a manlumm eowunglhaving mad-m portion, a faired a ing, a second over the one and having an opening closely fitted to said element, and a third segment secured to and similar to the first segment and defining therewith a segmental slot within which the sec- 0nd segment is movable.

10. In aircraft having an enlarged circular gun port, a spherical member fitted to the edge of the opening, rotatable relative to the aircraft and having an eccentric circular opening, and a second spherical member rotatably fitted to the edge of the opening of the first member having an eccentric opening for passage therethrough of a gun barrel, the position or the gun opening being adjustable radially andangularly by rotation of said members.

' edge to the tube and having an enlarged openl segment overlapping and movable 11. In aircraft having a circular gun port opening; a member fittedin said opening for rotation relative to the aircraftand having an eccentric circular opening; a second member fitted in said eccentric opening for rotationrelative to the first member, and having therein a gun opening eccentric to the opening of the first member through which gun opening a gun barrel may be passed, the position of the gun opening being adjustable radially and angularly by relative and joint rotation of said members.

ALFRED E. LEVENDOSKI. CHARLES F. ZIMMERMAN. RAYMOND P. HOLLAND, J R. 

